Flanookaph co



G. CASTAGNERIS.

WING ARRANGEMENT FOR FLYING MACHINES CARRYING GREAT LOADS.

APPLICATION FILED lAN.19| 1918- 1,3 18,845. Patented 0011.14, 1919.

INVE/VWR Guido Qmhgner/s A rro/ave'm G. CASTAGNERIS.'

WING ARRANGEMENT FOR-FLYING MACHINES CARRYING GREAT LOADS.

APPLICATION FILED JAN. Is. 1918.

1,318,845. Patented Oct. 14,1919.

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INVENTOI? 6 110 Cas/agn L's By M ATTORNEYS sumo 'cnsracrmms, or. ITALY.

" wmo Amuenmn w'r r012. rnmmmacnmns canmrmsemr Loans.

' To all wh omit may com-em:

Be it known that I, Gumo Cas'monnars, a subject of the King of Italy, residing at Rome, in the Kingdom of Italy, have invented new and useful Improvements in -Wing Arrangements for Flying-Machines Carrying Great Loads, of which the followmg '18 a specification. p

In aviation the problem of transport of great loads, and hence of flight to greatdis- 'tances is diflicult to solve on a account of passive resistance increases, or t certain inconveniences intrinsically inherent to the various forms of supporting surfaces adopted hitherto, the monoplane, the biplane, and the multiplane.

In-fact, with the monoplane surfaces, as

withthe biplane one,the ercentage of carried load diminishes as'the dimensions increase, since the weight of framework requisite for stifiening such surfacesrapidly increases. In addition to this, when, on increasing the dimensions 'of the said wing surface, and of power necessary for propulsion, usemust be made of several drivin plants separate units and distribut along the wing surfaces, the latter must be endowed with eater stiffness and strength and consequent must be heavier.

In the multip ane form, madeup'of several monoplane surfaces placedover each other, there exist, first and foremost, conditions of low eflicien for the intermediate surfaces on account 0 the perturbations in may suffer as little as possible from the in-,

finance of the two neighboring surfaces above and below respectively.

Such increased spacing out howeveryen tails a greater strength and i weight in the connecting frames, andin thesurfaces themselves, and augments the surface of the framework exposed to "the wind. On this account, also withf multiplane form as hithertoadopted and proposed, itis foundthat, with the increase in dimensions either the he percentage of transportable useful weight dimin- 'iSHBSIlOtBblYfilDd hence this form too gives unsatisfactory results when exceeding er. tain proportions.

Specification of Letters Patent.

Patented Oct. 14, 1919.

Application fled January 19, 1918." Seriallo. 212,764.

According to the present invention, the V obtain the maximum lifting power with a View of conveniently transporting great loads to great distances.

Such result is attained by assuming the biplane wing surface, instead of the monoplane, as the elementaryunit for the formation of the multiplane surface; the latter, thus resulting from several biplane wing surfaces, arranged either vertically or longitudinally at such intervals and in such relative positions as to practically reduce the perturbing influence to zero or' to a minimum. v

Theadvantage of employing biplane wing surfaces instead of monoplane is easily understood when the structure of the biplane surface with its trussed framework, in itself rigid,strong and light, is considered. The said structure allows of spacing out the biplane-surfaces as much as ma be required from each other and such wit out the need of reinforcing them, and this consequently allows the employment of simple and convenient connecting framework between any one biplane surface and the adjacent one, beneath or above,"in order to form the wing system which is the object of the present invention. I

I In the drawing appended herewith, which I illustrates difi'erent ways of combining the biplane elements for forming one multiplane according to the present invention,

Figure 1 shows, in front elevation, and in'plan, some forms of biplane wing adopted as elementary units in the aviatlon apparatuses according tothe present invention.

Fig. 2 shows, in front elevation, with a cross section at the side, one of the arrange-' ments' of the biplane elements adapted for forming the wing surfaceof the aviation apparatuses according to the present inventlon.

Figs. 3 and 4 show in front elevatlon, with sections beside, two ways of arranging groups of biplane surfaces and their connection together with their respectlve. frameworks. V

Figs. 5, 6, 7 show in side elevatlon three v faces arranged in alar columns.

Figs. 8,9, show in, Side eleyati gin in plan, and in section respectii elya format I faoes grouped togetherpnJamOIFe Forthe same object the two planes of 1 con 'stru' I.

tdethei an a brid e shaped supp rt. "i i ih'seetion anothe'i-form with biplane S111"- bridge shaped support.

rt'Figiplfland 11A: show in side elevation; and

out View; a" tot-m; a of constructionwith m'dge shaped support combined with alar {Figs 15 andlfi show Ein'plan two forms ozt eonstrnetion with alar eolumnswon' the tyg a' 101i thosein Figs.'5',,6,"7. j n r i a 1 7, and 318 aret partial sections inteaded toshow the'arrangement andot-vthe ear with respect-to the wing su'rfaees- Fig. 19 shows a particular formofi 60111166? tltt '=between,analar column andthe oar.

{In all-the identieal referemelet? similar eor'respondi 1g Y M SJ; 2% I rThe elementary unit with which the mill :tiplam wingsurfaoes are formed, according to the present invention; is "the ordinary b1- planecell efany; approved form, whether reotilineal, Fig. 1, 'a or bent at a diedral angle upward and downward, Figtl -a j-w,

mdeaeh otthese forms also'reptilipeaijin plan orarrow shaped as showninf these biplane elementsa is taken for getting the desired lifting power, and arranged into one or more distributing them in sueh. a manner that nelther by reason of the dastance or of their'mlmive position y m disturbve'ach.

.a 1 s distribut other The various elements ed are pnoperly connected: witheach other "and tothe car by means .of one orimore frameworks s'o arranged "as vto secure the maxim-am strength with theiminimum weight mid with the mmimum head .resistanoe; in older to insure freedom; of, the vaE-ibus elements from Treciprocaldisturbancer care mhst h taken thatwh n they-:are arren ed vex-t1callyyower each other the gap e Fig. '2,*be greater than the intervem a so imgdistanoe betweenthetwo planesof each dls If however the elements are not Harr i vertically oveneach other,ibut, placed behind each otherthen the distance must; be slibhthat 'each element following any other opefalls outof, the wakeof the foregmng one. distance is notably reduced by amnging the suoeessive elernents at difler-' rules vertically over one another and of' 135. l1, and 12 show inside elevation p p "and greater lifting power of" the'whole,

thelaforesaid v'ariouslength, decreasing from below up-' wardiifthe exam leof F; ."3; and decrees:

4:. The varieties of the length is from above wn'lwar example 7 with a. view of securinga better eifieieney I while diminishingfthe head resistance.

each cell instead of Mlitoeaeh other are-"0f fdiflerent depth, an preferably the inferior planes have mgij'eater depth, as is elearlyshown by the. seetionsaeeompanying the frontalviews of Figs. Band 4.

,The. different elements -,.a, ag,-

are connected by framework interposed as shown in Fig.5; or supported "over-hanging "as shown in ,4. v These rangements, the advantage sensing the enter ofvpressure. on thesail area with ro I gravity; and of! furthermore limiting the dlsplaoes'pect; toethe air-crafts eenter ofi ments of the center (if-pressure in the oeei'l lationsoi the apparatus; ati the time reducing the frontal projected l" area. i a i v .5

This arrangementhas the peculiar advan t ge of great lightness and thighenem which permit it aqload o0nsider'-' ably greater than wan be done with --the dieated that ordinary mbnflplane for biplane, B 'fW 'S 0 I equal I Y If the, loadt0 be was math is creased, it v:isnot desira le fto augment the number-50f 1 surfaoes superposed" overveach other lgvertieally, "or, their frontal wing f p ll itd, in I order to mNOida necessity [of reat height in theshedaandH eng rsyand th il" of wmg preadot the several alt-is mther desirable; to make use of two, three, will "morejgnoups ,ns; thosefin Figs, 3 and 4,0onne0t1n'gE-then topeach other and '40-- 6;0&r' rv-, es'iss wain Fights, 6,

'W i g g eueh way s to 90011 s ltate avsyst m anal gous tee vessele mastmg, tak ng? note that the distance di -2,

bet een he severalzgm psw besutficient I to" avmd' e d s u bing t influence et the: I

wh hlad on "thosewwhiehfifollqw,

and noting "also that 'thealements 10i" the a gro ps be 'plaeednlif a ibl at difi ereritwheights and ncidences?? arranged in one "or more;

Th b plane elements; efwlmeii g igrohpe or if 22 columns '-r.-, may be distributed in various planes 'p," and then the framework uniting them takes the form: ofha single bridgev truss strengthened by other connecting beams m-- fastened, to the .cars body when the dimensions so require,

as shown in Fi 8 and- 11. I In such com inations, and also in the columnar ones, biplane elements may likewise be arranged on the'cars'sides themselves, as shown in- 0aof 8, 10, 11,

-s" of elements as those in Figs. 5, 6,

7, and hence is obtained the construction shown in Fig. 14. a

As is evident, the arrangementof biplane surfaces into several groups allows these surfaces to be distributed, with respect to the car, in such a. way as to balance the weights concentrated in the'hull, by reducing the strains to, which .the latter is subjected to their minimum and hence securing the maximum of, stability.

The "car takes different shapes according to the number [and arrangement of the groups of lifting surfaces, as will be noticed for example in plan in Figs. 15 and 16, in which figures the arrow -sindicates the direction of movement. Said figures refer to aeroplanes with wing columns of the type shown in Figs. 6 and 7, in cross section in the 10, 12, 13, 17, '18 and in longitudinal section in Figs. 5, 6, 7, 14.

The wing system thus arranged, and fastoned to the car, is fitted in the usual way with longitudinal, transverse and vertical stabilizing means designed-for allaying and reducin the air-crafts pitching and rolling, the era being already stable in itself.

Such means may be, according to the purpose aimed at and-to the circumstances, the warping of the wings, articulated wing tips,

or otherm'ovable wing-parts, and-verticaldiaphragms either movable orfixed, none of which is here necessary to describe particularly as they are all well known in the art and not forming part of the present invention.

It may however be noted that the frame works m which act as connecting and stiifening members of the biplane wing elements, can be made to act also as supports in the formation of the diaphragms and stabilizing surfaces in the same manner as is done with the cellular stabilizing surfaces used in dirigible balloons.

For longitudinal stability, and depth control wing elements -t are employed, either mono lane or biplane suitably arranged, sing e, as shown in Figs. 5, 8, 11, or multiple as in Fig. 6, and even combining single and multiple elements together as shown in Fig- 7, which refers to the case of an aeroplane with fore and aft rudders.

Again, it will beunderstood that an entire wing-column, arranged at the fore or at the aft end may be made to act as an elevationrudder, and in this case it must be connected to the car by means of an articulated joint which allows of it being inclined backward or forward as shown in Fig. 19, where the column sis movable around a shaft -gresting on a suitable support so that the incidence of the wing surfaces may be varied at will.

Finally, as shown by way of example in Fig. 14, all the wing columns s- -.-s" -'-8"- may be made movable around shafts g-, -q, 1" so as to be able to vary the incidence simultaneously or singly.

This arrangement also allows the lifting power of the wing surfaces to be varied within wide limits.

For steering in the horizontal plane the vertical rudder -g-. is made use of, the game s4uitably placed as seen in Figs. 5, 6,

The driving plant may comprise either a single motor acting on a propeller placed in a convenient position in the longitudinal middle plane, insuch a manner that the propellers axis coincides with:the resultant of the head resistance as shown for example in Figs. 5, 6, 8, 11 or several motors suitably placed with. respect to the wing system, as shown in Figs. 7, 14:, 15, 16.

With regard to propellers, the most convenient combination is that of few screws .--e-- of large diameter arranged with their axis in the longitudinal middle plane, and, if in couples, symmetrically on the two sides of said plane rotating in reverse direction and at a convenient distance from the wing planes which precede them, in such way that they may work inthe least possibly disturbed air.

The screws themselves may be brought to contribute to the air-crafts steering both for direction and for altitude by adding their action to that of the rudders.

For the above said purpose puller screws are placed at the fore end and pusher screws at the aft end, at the same time providing means whereby the direction and inclination of their axis may be altered at will, so that their action be added to that ofthe rudders for rendering evolutions and maneuvers more rapid and easier whether in the horizontal plane or in the vertical one. Whenhull. of the car suitably "formed as a boat for their: floating water as: "shown. in Figs: 7 1, 14 with either smooth or stepped bottom. "Claims: 1 1,111 aincraft, a supporting wing system several biplane elements laced over one another column-wise and a rainework in columnshape connectedat itslo'wer entremity'to the body ogfthe cartowhich latter'the biplane elements are fastened, the vertical distance between any two adjoining biplane elementsbeing always greater than the interval separating. any-two planes. of oneelement. 1 a v In aircraft asupporting wing system comprising a plurality of biplane elements placed over one another column-'wiseFanrl framework connecting said biplane elements so: as to form in the whole a wing column fastened at the lower ends to the car the vertical distance between any two adjoiningibiplane elements being always greater; than the interval separating any two planes; of an element. a p I a v 3. In aircraft, a supporting wing" system, comprising several wing columns each con nected at its lower extremity with the, car and each column having a pluralityiof biplane elements arranged Vertically one above another, the distance between them being always greater than the interval,

separating anyttwo planes ofan element. 4. Inair-craft a supportin "wing system comprising a bridge framewor conveniently connected at its'lower extremities with the body of the car, of wing "columns connected intermediate of their ends with the bridge friamework, and of biplane elements :ar rimnged one over another and carried by I the wing columns, the space between adjacent biplane elements being greater thantthe space between the uppper and lowerpl'anes of each element.

b. In an aircraft, a bridge frame w'vbrk having its ends securedtto the bodyjofxthe cargbipl ane elements secured to the frame work, a wing column oonnected'with the bridge frame work, and a plurality of biplanes carried by ithe column one above other, the spgce between adjacent biplane elements: ing greater than the space betweenthe upper and lower planes-"of eachelement. m I

mounted "on the :"ofvthe ear, a plurality latter case,; as s eaplanes, they will have the 6.11 11 ansimmme bridge-theme work 65.

otbiplane. elementsykcarriotl .wby 'flthejsaid frame work; a plurality of wing" columns ypivotallywconnelcted'vwithpthe: bridge: frame work and a plurality of; biplaneelements.

secured to eachkcolltmnoneabbve theothev,

V the space' between adjacentbip-laneelemehts being greater than the) space between :the

up '1' and'lower planestof element; a :1 v

E .In aircraft, -a-= bridge-drama, work mounted on the body of the car, ap'lurality of biplane elements Carried by the sai frame work, a plurality of wi gc01u ns0f unequalheight wand pivotally .mounteidlon the frame? work intermediate of their ends,

and a filuralityzofbiplane elements carried a by eac column one above'the 'other,-the space between adj acent bilane elements wbe ing g eater than the special and lower planes bieanh elemen a N8. In air-craft. with a, supporting wing system comprising biplane elements con: nected with: eachqpther by means of fI-flmfif werk rf ste edi the car, s g column o of the linked at one extremitylto -t eb, H '1 car, a plurality of 1biplane elements eonnected with the said columnyand means for Varying the wing;eolumns inolination and hence varying he incidene oi e s rf c of-the biplanes, the space between adjacent biplane elements being greater than the space between the upper and lower planes ofeachi-elementq."

etween'the upper 9. In air-craft} with a supporting wing system comprising, biplane elements con? nected by :means of frameworks faastened to thecar a bridge framework connected at-its lower extremities with :the ear, a plurality of wing columns carrying biplanelelements connected to the bridge, framework, and means-for varying the inclination of the wing columns; an hence; varying the incidence-ofthe surfaces of the bi 1anes, the space between. adj acent biplane we ements be- .ing' greater than the space between the upper,

and lowergplanesof'each element a v In testimony whereof I have afiixed;

signature inithe presence of. two witnesses, tit/Rome;this l8th ;giay 9f 1917, GUIDO CASTAGNERISL --Wi .neSBes=- a LETTERN Lansoo'rm, v

:AUo sTo EGGENSCHMITZ'.

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